MAE 3241: Aerodynamics and Flight Mechanics Name: ______
February 11, 2005 Exam #1
Exam is worth 100 points and has 4 questions (30/30/25/25). Read each question carefully and show all your work.
Question 1 (30 Points):
An F-4 Phantom is being refueled in mid-air by a KC-10 Tanker. The refueling boom enters at an angle of 30º from the F-4 flight path. The fuel flow rate through the boom is 20 kg/s at a velocity of 30 m/s relative to the two aircraft. The density of the jet fuel is less than water, and is about 700 kg/m3. What additional lift force is necessary to overcome the force on the F-4 fighter due to the momentum transfer during refueling?
Question 2 (30 Points):
We wish to operate a low-speed (incompressible, inviscid) wind tunnel so that the flow in the test section has a velocity of 200 MPH (90 m/s). Consider two different types of wind tunnels, (a) and (b):
a) A nozzle and a constant-area test section, where the flow at the exit of the test section simply dumps out to the surrounding atmosphere (no diffuser).
b) An arrangement of nozzle, test section, and diffuser where the flow at the exit of the diffuser dumps out to the surrounding atmosphere.
For both of these wind tunnels calculate the pressure differences across the entire wind tunnel required to operate them so that they have velocity of 90 m/s in the test section. The geometry of the nozzle inlet and test section is the same in both tunnels (a) and (b) and is 2.0 m2 and 0.4 m2, respectively. For tunnel (b) only, we add a diffuser down stream of the test section, and the diffuser has an exit area of 1.8 m2. What does this say about the value of adding a diffuser on a subsonic wind tunnel?
Question 3 (25 Points):
A steady, inviscid, incompressible flow has a velocity field given by:
Where f is a constant having the dimensions of 1/s. Derive an expression for the pressure field p(x,y,z) if the pressure p(0,0,0)=p0 and .
Question 4 (25 Points):
Consider the two-dimensional, incompressible velocity potential given below:
a) Is this potential function a solution to Laplace’s Equation? If so, what does it mean?
b) If it exists, find the stream function y(x,y) for this flow.
c) Find the equation of the streamline that passes through (x,y)=(2,1).
Extra Credit (10 points):
Only do the extra credit if you have completed the rest of the exam
Consider two different flows over geometrically similar airfoil shapes, one airfoil being twice the size of the other. The flow over the smaller airfoil has freestream properties given by T∞=200K, r∞=1.23 kg/m3, and V∞=100 m/s. The flow over the larger airfoil is described by T∞=800K, r∞=1.74 kg/m3, and V∞=200 m/s. Assume that the viscosity is proportional to T1/2. Are the two flows dynamically similar?
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